134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130...

7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008

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TO 1C-

TECHNICAL MANUA

FAULT ISOLATION

ORGANIZATIONAL MAINTE

PROPELLERS


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LIST OF EFFECTIVE PAGESNOTE: The portion of the text affected by

outer margins of the page. Chapointing hands.

Dates of issue for original and changed pages are:

Original. . . . . . .. . . .. . . .. . . .. . . .0 . . . .. .1 Februar y 2002 Cha nge.. . . . .. . . .. . . .. . . .. . . .. .Cha nge. . .. . .. . .. . .. . .. . .. .. . ..1 . .. .15 F ebruary 2003 Cha nge. . .. . .. . .. . .. . .. . .. . .. . .Cha nge.. . . . .. . . .. . . .. . . .. . . .. .2 . . . .. . . 15 August 2003 Cha nge.. . . . .. . . .. . . .. . . .. . . .. .Cha nge. . .. . .. . .. . .. . .. . .. .. . ..3 . .. . .. . 1 J anua ry 2004 Cha nge. . .. . .. . .. . .. . .. . .. . .. . .

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 694, CONSISTING OF

P a ge *Cha nge P a ge *Cha nge P a g

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TABLE OF CONTENTS

Section/Paragraph

LIS T OF TAB LE S ...........................................................

LIS T OF SC HE MATIC DI AG RAMS .............................

INTRODU CTION ............................................................

P urpose.........................................................................U sefulness ....................................................................Sa fety ............................................................................Arra ngement ................................................................Special I nst ructions for Open C ircuit B rea kers........S i l I t ti f Sh i ld d Wi


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LIST OF TABLES

Section Number Title

I I 2-1 P ropeller M alfunct ions ........................................ 66

I I 2-2 P r opeller S yst em Fa ult C odes ............................ 6

I I 2-3 P ropeller Fea ther S yst em Fa ult C odes .............. 6I I 2-4 Nega t ive Torq ue S igna l S yst em F ault Codes .... 6

I I 2-5 P ropeller Low Fluid Wa rning S yst em Fa ultCodes (Airpla nes P rior t o AF92-0547 andAF92-3021 Thr ough AF92-3024)...... .... .... .... ... 6


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LIST OF SCHEMATIC DIAGR

Number Title

2-6 Be t a I n di ca t i on E l ect r ica l Sch em a t i c D i a gr a m (Ai rand Airplanes AF92-3021 Through AF92-3024)

2-7 Be t a I nd ica t i on E lect r ica l Sch em a t i c D i a gr a m (Ai rThr ough AF92-2104 a nd Airpla nes AF92-3281 a

2-8 Neg a t iv e Tor q ue S i gn a l Sy st em E lect r ica l Sch em aP rior to AF92-0547 a nd Airpla nes AF92-3021 ThMC-130H Airplanes).............................................

2-9 Neg a t iv e Tor q ue S i gn a l Sy st em E lect r ica l Sch em aAF92 0547 Thr ough AF92 2104 a nd Airpla nes A


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INTRODUCTION

PURPOSE. This publica tion conta ins fa ult isola tion procedurtion of the C-130 propeller system.

USEFULNESS. The effectiveness of this publication shall, topart icipat ion in t he program by operat ions a nd ma intenan cetion Manua l. U ser feedback is the most important factor if tto-da te. U se the AFTO Form 22 system to recommend n ew ation in this publication.

SAFETY. Fault isolation procedures in this publication are abrief an d concise. Comply w ith War nings a nd Ca utions to prAlways turn off the external power selector switch (located oan y overhead panel. Refer to the ma intenan ce ma nua ls (J obprocedures - always bring the airplane to a safe condition bef


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E S S E ssent ia l

FIM Fa ult isola t ion ma nua l

FLT E NG R Flight engineer

FRM Fa ult report ing ma nua l

FU S S TA (FS ) F usela ge st a t ion

G RD G round

G round fa ult Mea sura ble ground w hen t here should be

H ot fa ult Mea sura ble volt a ge w hen t here should be

LRU Line repla cea ble unit

MACAWS Mode a dvisory ca ut ion a nd w a rning syst em

NTS Nega t ive t orque signa l


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Section I. GENERAL INFORM

1-1. GENERAL. The C -130 propeller sy stem fau lt a na lysis composed of tw o elements: the Fa ult Report ing Ma nua l (FRM(FIM).

NOTE

Ground maintenance crews may also use FRM in Section XX of TO 1C-130H-2-00FR-00-1 or C130(M)H-2-00FR-00-1) to gain the same result

following para gra ph.1-2. FAULT REPORTING MANUAL (FRM). Flight crews usena nce personnel a bout ma lfunctions th e flight crews encountdures, the flight crew ma kes checks a nd observa tions to helptha t deal w ith symptoms and condit ions occurring a t th e t im


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c. Faul t C ode Indexes. The faul t code indexes l is t a l l appl icablenumerical order. Ea ch fau lt code represents a peculia r malfun ctionw hich could be encountered by th e flight crew. A figure an d block ncode tells where to go in the fault isola tion diagra m to sta rt t he actua ssigned fa ult code num bers betw een 6110001 a nd 6120999 represesynchrophaser system failures, and are subdivided as follows:

SYSTEM/FAILURE ASSIGNED FAULT

P ropeller syst em 6110001-6110008, 6

P ropeller fea ther system 6110010-6110017, 6

Nega t ive t orque signa l system 6110020-6110024, 6

P ropeller low fluid w a rning syst em 6110030-6110034, 6


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sequence in the same manner until every block in the figure blocks in the same figure with the same number).

(3) Fa ult Codes. Any number in the upper right corneblocks w ill not ha ve a fault code in them, an d a few w ill contnumbers are used to make sure troubleshooting starts at the code in dex.

(4) Test Points . A block may conta in a test point syming wh en an electrica l measurement is specified. A note idenw hich the test point is locat ed. The test points on a schematlocat ion of th e mea surement being ma de. Test point num bercorner of th e schemat ic diag ra m. Test points 2 a nd up th en a clockwise rota tion. A single test point reference for volta gevoltage is referenced to airplane ground.

(5) Circuit Int erruption Symbol. A lightning bolt withcircuit interruption symbol ( ). I ts presence means tha t a l


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1-4. SPECIAL TOOLS AND TEST EQUIPMENT REQUIRED FOR FA

AN typedesignation

Nomenclature or part No. Alternate

Synchropha ser system AD 33480-2 E quiva lent

test set

Mult imet er AN/P S M-37( ) E quiva lent

28 VDC light Loca l ma nufa cture E quiva lent

Shim (0.225 inch Loca l ma nufa cture E quiva lent


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Section II. PROPELLER ASS

2-1. GENERAL. The fault isolation material in this section propeller system ma lfunction excluding th e synchropha ser syinclude a m a lfunction in dex, fault code indexes, prepar a tion fault isolation, fault isolation diagrams (the actual troubleshotions for ha rdwa re referenced in the fault isolat ion diagra ms

2-2. MALFUNCTION INDEX. The ma lfunction in dex (ta ble 2encountered during ground ma intenan ce and n o numeric fauFRM dia gram , wh en no numeric fault code wa s provided by

crew only provided an a lphan umeric fault code. Ma lfunctionlisted in the left column of the ta ble. The middle column conwhile the right column identifies the preparation and fault is

Table 2 1 Propeller Malfuncti


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Table 2-2. Propeller System Fault Codes - Con

Fault code AFTO Form 781A report F

6110002 Be t a i nd ica t or li gh t No. (1)(2)(3)(4) f a il ed P e r for m f

to come on in (br ight )(d im)(both br ight go to f igu

and dim) modes when throttle was re-Airplanes

ta rded below FL IG HT ID LE /FLT ID LE3021 thro

gate.

block 74

block 13

block 80

Airplanes

and AF92

block 76


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Table 2-3. Propeller Feather System

Fault code AFTO Form 781A report

6110010 P r op el ler No. (1)(2)(3)(4) f a il s t o g o f rom P e

m a xi mu m r ev er se t o ful l f ea t h er i n 25 g o

seconds.

6110011 P r opeller fea t h er ov er ri de b ut t on lig ht / R

FTHR light No. (1)(2)(3)(4) fails to go off

at end of feather cycle.

6110012 P r opeller fea t her over ride but ton No. P e

(1)(2)(3)(4) f a il s t o pop ou t a t e nd of g o

feather cycle.

6110013 P ROP ELLE R FE ATH ER OVE RRID E N


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Table 2-4. Negative Torque Signal System Fault Code

Fault code AFTO Form 781A report F

6110021 E n g in e No. (1)(2)(3)(4) ex hi bi t s ex ces si ve P e r for m f

NTS indications in relation to other oper- go to figu

ating engines.

6110022 F EATH E R VAL VE AND NTS CH E CK P er for m f

l ight/NTS light No. (1)(2)(3)(4) fai led to go to figu

come on when air start was accom-

plished.

6110023 F EATH E R VAL VE AND NTS CH E CK P er for m f

l ight/NTS light No. (1)(2)(3)(4) fai led to go to figu

come on when engine condition lever was

moved t o FE ATH E R/FTR posit ion


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Table 2-6. Propeller Low Fluid Warning System Fault Codes (Airand AF92-3281 and Up)

Fault code AFTO Form 781A report

6110030 P ROP low oil w a rning light No. F

(1)(2)(3)(4) fails t o go to selected bright / 1C

dim mode. co

6110032 Wit h kn ow n low pr opeller flu id q ua n t it y , P e

P ROP low oil w arning light No. go

(1)(2)(3)(4) fa iled t o come on.

6110034 P ROP low oil w arn ing light No. P

(1)(2)(3)(4) ca me on. go


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2-5. FAULT ISOLATION DIAGRAMS. The fault isolation diatr oubleshooting a ny propeller malfun ction. When th e flight creport a ma lfunction, th a t num ber will be found in one of the

fault code is available, the malfunction index identifies the fi

a . Arrangement . One faul t isola t ion d iagram is includedsecond for th e propeller low fluid wa rnin g system. Opposite diagra m is a n il lustrat ion w hich shows th e physical locat ion fau lt isola tion diag ra m blocks. Double-check these illustra tiowh en making an observat ion or measurement . Following th eelectrical schema tic diag ra ms. The schema tic diag ra ms ar e ldiag ra m is covered up when folded out for use. Thus it is ea

nents, circuits, a nd t est points t ha t a re referenced on t he faub. Using Troubleshoot ing Data . A thorough descr ipt ion o

other troubleshooting data is provided in Section I. In a dditiillustra ted how-to-use figure for this section. U nderst a nd homa tion before at tempting to repair the a irplan e


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1 6110F01, 6110N01,2

6110P01 YES NIs BETA indicator light on bright-

Is airplane equipped with BETA ly?indicator lights (1)?

NOYES

3

YIs airplane serial number AF92-0547 through AF92-2104 orAF92-3281 and up?

NO

4

Momentarily place CAUTION


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FROM SHT 1

9 6110017

CAUTIONIf PROPELLER FEATHER OVER-RIDE button does not pop out 4to 5 seconds after propeller blademovement stops, pull out manual-ly to prevent damage to auxiliarypump motor. NO

TO SHT 57a. Place FEATHER VALVE ANDNTS CHECK switch (3) toVALVE.

b. Move ENGINE CONDITIONlever (1) to FEATHER.Does PROPELLER FEATHEROVERRIDE button (2) pull in andremain in?


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FROM SHT 1

11 16

NO NOIs airplane prior to AF95-1001 or is Swap torquemeter indica-torquemeter BETA legend (2) pre- tors.sent on indicator? Does malfunction persist?

YES YES

12

a. Place the NORM/NVIS switch (8)


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FROM SHT 7

28

Did FTHR light (3) go off when NOpropeller feather override button(5) popped out?

YES

29 NOTO SHT 75

Is BETA indicator light (2) off?

YES

30 6110024

a If troubleshooting fault code


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FROM SHT 7

34

Place FEATHER VALVE AND NTS CHECKNOswitch (5) to NTS. TO SHT 123

Is FEATHER VALVE AND NTS CHECKlight (4) on?

YES

35

Move ENGINE CONDITION lever (3) to NOGROUND STOP. TO SHT 125Is FEATHER VALVE AND NTS CHECKlight on?

YES


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FROM SHT 9 OR 11

37

CAUTIONDo not move throttle and do not move engine condition lever toward FEATH-ER/FTR position while shim is installed. Damage to propeller assembly couldresult. NO

a. Gain access and insert a 0.225-inch thick shim between engine NTSplunger (1) and engine negative torque bracket/lever adjustment screw (2).b. 1 2 3 Place FEATHER VALVE AND NTS CHECK switch (5) to VALVE.c. Hold engine condition lever (7) in AIR START.Did propeller blades (8) move toward feather position?

YES

38

40


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TO 1C-130H-2-61FI-00-1

FROM SHT 13

44

a. Connect synchrophaser systemtest set in accordance with Prepa-ration B.b. Start engine under test andsymmetrical engine in accordancewith TO 1C-130H-2-71JG-00-1,

NO71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.c. Perform torquemeter calibrationin accordance with TO 1C-130H-2-77JG-00-1, 77-10-04; or TO 1C-

130(A)H-2-71JG-00-1, 71-00-10.Is torquemeter calibration satisfac-tory?

YES


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FROM SHT 17

61

a. Move throttles (3) to MAXIMUM

REVERSE/MAX RVS.b. Record indications on engine

YEStorque indicators (2) and RPM in-TO SHT 161

dications in test set FUNCTIONdisplay (1).Is there a symmetrical torque dif-ference in excess of 1000 inch-pounds?

NO

62


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FROM SHT 196

S65w

Did pitchlock disengage in accordance with

1NOTO 1C-130H-2-61JG-10-1, 61-10-02 (as indi- 0cated by torque and RPM reading same as

1initially recorded in the pitchlock check)?

reTYES

66

a. Perform synchrophaser index in accordance

with TO 1C-130H-2-61JG-10-1, 61-10-02 (sub-task 1-2-6). NOb. Move throttles (3) to GROUND IDLE/GND TO SHT 167IDLE.Do propeller low pitch stops retract as indicat-


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FROM SHT 1

7371

YES YESIs airplane serial number AF92-Are all BETA indicator lights

0547 through AF92-2104 or(1) on dimly? AF92-3281 and up?

NONO

74 6110002

Gain access to terminals of indi-cator lights dimmer No. 10 (2).

NOIs 28 VDC present between dim-

mer terminals W and X?1 2

YES


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FROM SHT 23

81YES

Is airplane AF92-0547 through TO SHT 27

AF92-2104 or AF92-3281 and up?

NO

82 6110002

YESPress to test affected BETA indi-TO SHT 31

cator light (1).Does light press to test?

NO

83


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O


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FROM SHT 25

96

Is 28 VDC present on specified

terminal of indicator lights dimmerNo. 10 (5)?

Dim TestProp Term Point

NO

1 j3

2 k5

3 m7

4 n9

YES


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FROM SHT 31

111

a. Connect plug P390 (3) to valve housing assembly (4).

b. Gain access to and disconnect plug P398 (2) at engine fire-wall.

NOIs there continuity between pins H and V of receptacle J239 (1)?

28 29,

30 31,

32 33OR

35 36

YES

112YES

Is airplane serial number AF92-0547 through AF92-2104 or TO SHT 35AF92-3281 and up?


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TO 1C 130H 2 61FI 00 1

FROM SHT 33

118 YESTO SHT 37

Is airplane AF95-1001 and up?

NO

119

a. Remove power from airplane.b. Gain access to and disconnectplug P1725A (1) from systemscaution/advisory panel.Is a ground present on the speci-fied pin of plug P1725A?

NOPlug TestTO SHT 37

Prop Pin Point


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TO 1C 130H 2 61FI 00 1

FROM SHT 35

121

NOIs an outboard propeller beingtroubleshot?

YES

122

Gain access to and disconnectplug P130/P1139 (4) at outerwing break.Is a ground present on specifiedpin of receptacle J235/J935 (3)?

NO


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FROM SHT 33

126


YES

127

Gain access to and disconnectplug P130 (4) at outer wing break.Is a ground present on specifiedpin of receptacle J235 (3)?

NO


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FROM SHT 1

131 6110002YES

Are any BETA indicator lights (1)

on dimly?

NO

132

Gain access to terminals of indi-cator lights dimmer No. 10 (2).

YESIs 28 VDC present between dim-mer terminals W and X?

1 2

NO


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FROM SHT 1 OR 5

136

Gain access to and inspect en- YES

gine NTS plunger (2).Is plunger actuated?

NO

137

a. Inspect NTS linkage for correctgap of 0.011 to 0.020 inch in ac-cordance with TO 1C-130H-2- YES

61JG-20-1, 61-20-22.b. Also inspect linkage for anybinding or damaged components.Are any discrepancies found?


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FROM SHT 45

153

a. Remove power from airplane.b. Gain access to and disconnectplug P1725A (2) from systemscaution/advisory panel.Is a ground present on specifiedpin of plug P1725A?

NOPlug Test

Prop Pin Point

1 5378

2 5479

3 5580


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FROM SHT 45

160

a. Place FEATHER VALVE ANDNTS switch (3) to NORMAL.b. Gain access to terminals of

164YES NNTS check relay (2) and discon-nect wire from relay terminal A2. Is airplane an MC-130H?Is a ground present on discon-nected wire?

52,

22,

59OR

29

NO

YES

TO SHT 51

161


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FROM SHT 49

170

Gain access to and disconnectplug 47404A2P1 from indicatorlight dimmer No. 4 (1).Is a ground present on specifiedpins/receptacle points?

Pins Test Points

1069

2470

NO

23

71

2272

373


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FROM SHT 1

173

a. Open PROP SYNCHRO

PHASER and SYNCHRO YESPHASER circuit breakers (5,4).b. Gain access to and disconnectplug P390 (6) at valve housing


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FROM SHT 53

177

a. Place FEATHER VALVE AND NTSCHECK switch (3) to NORMAL.

b. Gain access to NTS check relay (2) YESand disconnect wire from relay terminal B2.Is a ground present on relay terminal B2?

51,

21,

58OR

28

NO

178

Disconnect wire number _K603A from relayterminal X1. YESIs a ground present on disconnected wire?


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FROM SHT 3 OR 5

186YES

Does propeller feather override TO SHT 63button (2) cycle?

NO

187 6110015

a. If troubleshooting fault code6110015, move engine conditionlever (4) to FEATHER/FTR. 188

NO Yb. Momentarily press propellerIs fault code 6110017 being

feather override button (2). troubleshot?1 3 4 Does light in button comeon while button is pressed?

2 Does FTHR light (5) come onNO


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FROM SHT 57

192

a. Move engine condition lever (3)to GROUND STOP/GND STOP.

b. Remove power from airplaneand gain access to terminals of NOpropeller feather override button TO SHT 61(2).Is a ground present on button ter-minal 7?

23

YES

193


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FROM SHT 59

198


YES

199

Gain access to and disconnectplug P124/P1134 (1) at outerwing break. NOIs a ground present on pin V of


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FROM SHT 57

203 6110014

Gain access to and inspect propeller feather override button (3) for YEScorrect jamnut installation, and loose or damaged connections.

Are any discrepancies found?

NO

204

a. Move engine condition lever (4) to GROUND STOP/GND STOP.b. Open FEATHER PUMP MOTOR PHASE A,B,C/ 4 FEATHER PUMPMOTOR circuit breakers (1). NO

c. Gain access to terminals of feather relay (2) and disconnect wirefrom relay terminal X2.d. Move engine condition lever to FEATHER/FTR.Does propeller feather override button pull in and remain in?


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FROM SHT 57

215214

NO NPull fire emergency handle (1).Is fault code 6110016 being

Does propeller feather overridetroubleshot?

button (3) pull in?YESYES

216

a. Gain access to terminal boardTB146A (4).b. Move engine condition lever (5)to FEATHER/FTR.

Is 28 VDC present on specifiedterminal?

YTest


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FROM SHT 65

219

a. Remove electrical power fromairplane.

b. Gain access to terminals of en-gine condition lever feather con-trol switch (1).Is there continuity between switchterminals 1NO and 2NO?

NOTest

Prop Sw Points

1 S86E40 39

2 S86F40 39

3 S86G40 39


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FROM SHT 3 OR 5

227 6110013224

Momentarily hold MACAWSYES NIs airplane serial number AF92-LAMP TEST switch (3) in test po-

0547 through AF92-2104 orsition.

AF92-3281 and up? Does applicable light come on?

NOYES

225 6110013

Remove bulb from affected PRO-


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FROM SHT 69

233

a. Remove electrical power fromairplane.

b. Gain access to and disconnectplug P1725A (2) from systemscaution/advisory panel.Is a ground present on applicablepin of plug P1725A?

NOPlug Test

Prop Pin Point

1 4560

2 4662

3 4763


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FROM SHT 69

236

Gain access to and disconnect plug47405A1P1 from indicator light dimmer No.

5 (1).Is there continuity between specified pin ofplug 47405A1P1 and terminal G of the ap-plicable PROPELLER FEATHER OVER-RIDE button?

NOProp Pin Test Points

1 1151 27

2 1252 27

3 1353 27

4 2554 27


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FROM SHT 7 OR 9

241 6110008

NOTEPerform steps a and b only iftroubleshooting fault code6110008.

a. Move throttle (6) aboveFLIGHT IDLE/FLT IDLE gate.b. Hold engine condition lever (7) YES

in AIR START position until pro-peller blades (2) are above flightidle.

c. Open PROP SYNCHROPHASER and SYNCHROPHASER circuit breakers (5,4).d Gain access to and disconnect


107/693

TO 1C-130H-2-61FI-00-1


108/693


109/693

TO 1C-130H-2-61FI-00-1


110/693

FROM SHT 77

252NO

Is an outboard propeller being

troubleshot?

YES

253

Gain access to and disconnectplug P130/P1139 (4) at outerwing break.

Is a ground present on receptacleJ235/J935 (3) pin?

NO


111/693

TO 1C-130H-2-61FI-00-1


112/693

FROM SHT 77

257NO


troubleshot?

YES

258

Gain access to and disconnectplug P130 (4) at outer wing break.

Is a ground present on specifiedplug pin?

NO


113/693

TO 1C-130H-2-61FI-00-1

FROM SHT 7


114/693

FROM SHT 7

262NO

Did propeller blades (1) move to- TO SHT 85ward feather position at all?

YES

263

a. Open FEATHER & AIR STARTcircuit breaker (2).b. 1 3 Open PROP LOW OILLEVEL circuit breaker (3).c. 2 Open MACAWS PILOT, CO-

PILOT and CONTROL circuitbreakers (4,5,6,7,8).

YESd. Gain access to and disconnectTO SHT 95


115/693

TO 1C-130H-2-61FI-00-1

FROM SHT 83


116/693

FROM SHT 83

267

1 3 4 Is FEATHER VALVE AND NONTS CHECK light (3) on?

2 Is NTS light (6) on?

YES

268

YESWith engine condition lever (5) inTO SHT 87

FEATHER/FTR position, is auxiliarypump motor (1) running?

NO


117/693

TO 1C-130H-2-61FI-00-1

FROM SHT 13 OR 85


118/693

FROM SHT 13 OR 85

274

a. If pulled, push in fire emergency han-dle (3).b. Move engine condition lever (2) toGROUND STOP/GND STOP.c. Gain access to and disconnect plug NOP410 (4) at auxiliary pump motor. TO SHT 91d. Move engine condition lever toFEATHER/FTR.Is 115 VAC present on plug pins A, B,and C?

15 16 17

YES


119/693

TO 1C-130H-2-61FI-00-1


120/693


121/693

TO 1C-130H-2-61FI-00-1

FROM SHT 87 OR 89


122/693

286

288Gain access to feather pump mo-tor relay (4). Is 115 VAC present on relay ter-Is 115 VAC present on relay terminals A2, B2 and C2, or T3, T2,

NO Nminals A1, B1, and C1, or L3, L2, and T1 (depending upon terminaland L1 (depending upon terminal labeling)?labeling)?

3 2 1

8 7 6

YESYES

290

Rep


123/693

TO 1C-130H-2-61FI-00-1

294FROM SHT 91


124/693

FROM SHT 91Repair open circuit between affecteterminal of feather pump motor rela292

NOIs an outboard propeller be-

Plug Pining troubleshot?

A

BC

YES


125/693

TO 1C-130H-2-61FI-00-1

FROM SHT 83


126/693

297

a. Connect plug P392 (3) to pro-peller control.b. Gain access to and disconnect

NOplug P396 (2) at engine firewall.Is a ground present on pin F ofreceptacle J241 (1)?

49

YES

298

Gain access to terminal boardTB107 (4) and disconnect speci-


127/693

TO 1C-130H-2-61FI-00-1

FROM SHT 7


128/693

302 6110012303.1

a. Move engine condition lever (6) to FEATH-Reseal

ER/FTR.cordanc

b. After propeller blades (1) have reached

61-10-1NOfeather position, check for internal leakage by accordaholding propeller feather override button (4) in

61-10-1while listening for a loud squeal from respec-

cordanctive propeller assembly.

61-10-1Is a loud squeal heard from propeller?

YES

302.1

a. Open affected FEATHER PUMP MOTORPHASE A,B,C/ 4 FEATHER PUMP MOTOR


129/693

TO 1C-130H-2-61FI-00-1


130/693

FROM SHT 97

306

a. Open PROP SYNCHRO PHASER and SYNCHRO PHASER cir-YES

cuit breakers (6,7).b. Gain access to and disconnect plug P390 (9) at valve housingassembly.Does propeller feather override button (5) pop out?

NO


131/693

TO 1C-130H-2-61FI-00-1

FROM SHT 99


132/693

314

Gain access to terminal boardTB107 (3) and disconnect speci-fied wire from terminal 1.

Is a ground present on discon-nected wire?

Test YESProp TB Wire No. Point TO SHT 103

1 TB107S 1K76C1848

2 TB107T 2K76B1848

3 TB107U 3K76B1848

4 TB107V 4K76C1848


133/693

TO 1C-130H-2-61FI-00-1


134/693

FROM SHT 101

318NO


troubleshot?

YES

319

Gain access to and disconnect

plug P124/P1134 (3) at outerwing break. YESIs a ground present on plug pin


135/693

TO 1C-130H-2-61FI-00-1

FROM SHT 7


136/693

322.1YES

Is aircraft being troubleshot MACAWS equipped (AF92-0547 TO SHT 113thru AF92-2104 and AF92-3281 thru AF96-7325)?

NO

326

a. Open NTS CHECK circuit breaker (5).323 6110022, 6110023

b. Open FEATHER PUMP MOTOR PHASEa. If troubleshooting fault code A,B,C/2 FEATHER PUMP MOTOR circuit6110022 or 6110023, place breakers (6).FEATHER VALVE AND NTS c. Move ENGINE CONDITION lever (1) toYES

CHECK switch (4) to VALVE. FEATHER.b. Press to test affected d. Temporarily remove power from airplaneFEATHER VALVE AND NTS and gain access to terminals of FEATHER


137/693

TO 1C-130H-2-61FI-00-1

FROM SHT 105


138/693

330

Temporarily remove power fromairplane and gain access to termi-nals of ENG NO. 1 FEATHER

VALVE AND NTS CHECK light YES(1).Is 28 VDC present on light termi-nal 1?

6

NO

331

Temporarily remove power from


139/693

TO 1C-130H-2-61FI-00-1

FROM SHT 9 OR 105


140/693

337

a. Open PROP SYNCHRO PHASER andSYNCHRO PHASER circuit breakers (4,3).b. Gain access to and disconnect plug

340P390 (6) at valve housing assembly. NOIs there continuity between pins F and K of Is fault code 6110023 beingvalve housing assembly receptacle (5)? troubleshot?

41 43,

13 15,

66 68OR

38 40

YES

NO

TO SHT 119


141/693

TO 1C-130H-2-61FI-00-1


142/693


143/693

TO 1C-130H-2-61FI-00-1

360

a. Remove electrical power from


144/693

pairplane.b. Gain access to and disconnectFROM SHT 105 AND 111plug P1725A (2) from systemscaution/advisory panel.357

NO YIs a ground present on the appli-Is an outboard propeller beingcable plug pin?

troubleshot?

Prop Plug Pin Test Point

2 5479

3 5580

YES

NO


145/693

TO 1C-130H-2-61FI-00-1

FROM SHT 113

364


146/693

364

Momentarily hold the MACAWSLAMP TEST switch (1) in the test NOposition.

Does the applicable light comeon?

YES


147/693

TO 1C-130H-2-61FI-00-1

FROM SHT 111

367


148/693

367

Gain access to and disconnect plug47404A2P1 from indicator light dimmer No.4 (2).

Is a ground present on specified pins? 3

Light No. Plug Pin Test Point RNO

m1 1

764N

2 1675

3 1574

4 373

YES


149/693

TO 1C-130H-2-61FI-00-1

FROM SHT 21 OR 109

372 6110021


150/693

Gain access to and check NTS linkage for correct gap ofNO

0.011 to 0.020 inch in accordance with TO 1C-130H-2-61JG-20-1, 61-20-22.Is adjustment correct?

YES

373

a. Rotate propeller control (2) clockwise as viewed from therear and hold firmly against prop torque retainer assembly (6).b. Check clearance between torque retainer lug (3) and prop YEStorque retainer assembly for a maximum gap of 0.050 inch.

c. Release propeller control.d. Also inspect components for looseness or damage.


151/693

TO 1C-130H-2-61FI-00-1

385FROM SHT 105

Repair 381

ENG NYES


152/693

ENG NYESIs propeller No. 2 being troubleshot? CHECK

2 FEAT(2). (SNO

386382

Repair Press to test ENG NO. 2 FEATHER ENG NNOVALVE AND NTS CHECK light (2). CHECKDoes light press to test? 2 FEAT

(2). (SYES

387

Repair 383

ENG NYES


153/693

TO 1C-130H-2-61FI-00-1

FROM SHT 11

390


154/693

Gain access to terminals of NTScheck relay (1).

YESIs 28 VDC present on relay termi-nal A1?

54,

24,

61OR

31

NO

391

Is 28 VDC present on relay termi-YES

nal A2?

52,

22,

59OR

29


155/693

TO 1C-130H-2-61FI-00-1

FROM SHT 11

395


156/693

Gain access to terminals of NTS398check relay (1).

Is 28 VDC present between relay Is 28 VDC present on relay termi-YES Yterminals X2 and X1? nal A1?

49 50,

19 20, 54 ,

24,

61OR

31

56 57OR

26 27

NO

NO


157/693

TO 1C-130H-2-61FI-00-1

FROM SHT 125

404


158/693

Gain access to terminals ofFEATHER VALVE AND NTSCHECK switch (2). YESIs 28 VDC present on switch ter-

minal 3?

4

NO

405

Is 28 VDC present on FEATHER

VALVE AND NTS CHECK switch YESterminal 2?


159/693

TO 1C-130H-2-61FI-00-1

FROM SHT 125

409


160/693

NOTEPut meter negative lead on relay terminalB2.

a. Open FEATHER & AIR START circuit YESbreaker (4).b. Move ENGINE CONDITION lever (6) toFEATHER.Is a ground present on terminal B2 of NTScheck relay (1)?

51,

21,

58OR

28

NO


161/693

TO 1C-130H-2-61FI-00-1

FROM SHT 9

415

T il f i l


162/693

a. Temporarily remove power from airplane.b. Gain access to and disconnect plug P1725A(4) from systems caution/advisory panel.Is a 28 VDC present on applicable plug pin?

Plug TestProp Pin Point NO

1 5378

2 5479

3 5580

4 5681

YES


163/693

TO 1C-130H-2-61FI-00-1

FROM SHT 131

422

a Temporarily remove power from airplane


164/693

a. Temporarily remove power from airplane.b. Connect plug P1725A (4) to systems cau-tion/advisory panel.

NOc. Gain access to and disconnect plug P18/

P1835 (6) at outer wing break.Is 28 VDC present at pin N?

33OR

47

YES

423

a. Temporarily remove power from airplane.b. Connect plug P18/P1835.


165/693

TO 1C-130H-2-61FI-00-1

FROM SHT 131 OR 133

428

Gain access to valve housing re-


166/693

Gain access to valve housing re-ceptacle (4).Is there continuity between pins F

NOand K?

13 15,

38 40,

41 43, OR

66 68

YES

429

Gain access to and disconnectplug P398 (2) at engine firewall.

NO


167/693

TO 1C-130H-2-61FI-00-1

FROM SHT 129

433

NOTE


168/693

NOTEPut meter negative lead on recep-tacle pin E.

a. Connect plug P390 (3) to valvehousing assembly (4).

NOb. Gain access to and disconnectplug P398 (2) at engine firewall.Is there continuity between pins Eand F of receptacle J239 (1)?

45 44,

17 16,

64 63OR

36 35

YES


169/693

TO 1C-130H-2-61FI-00-1

FROM SHT 125

440YES

Is No. 2 propeller being


170/693

Is No. 2 propeller beingtroubleshot?

NO

441

Gain access to terminals of en-gine No. 2 NTS check relay (3).

NOIs 28 VDC present on relay termi-nal X2?

19

YES


171/693

TO 1C-130H-2-61FI-00-1

FROM SHT 9 OR 11

449

Momentarily hold engine condition NO


172/693

y g NOlever (3) in AIR START. TO SHT 143Does auxiliary pump motor (2) runwhile lever is held?

YES

450

4Inspect NTS linkage (1) for servicea-bility and check for correct gap of A

NO0.011 to 0.020 inch in accordance wwith TO 1C-130H-2-61JG-20-1, 61- 2

20-22. qIs NTS linkage satisfactory?


173/693

TO 1C-130H-2-61FI-00-1

FROM SHT 141

455

a. Gain access to terminals of


174/693

feather relay (2).b. Momentarily hold ENGINECONDITION lever (1) in AIR YES

START.Is 28 VDC present on relay termi-nal B2 while lever is held?

32

NO

456

a. Gain access to pedestal termi-


175/693

TO 1C-130H-2-61FI-00-1

FROM SHT 143

459

Open FEATHER & AIR START circuit breaker(4)


176/693

(4).Is there continuity between terminal 1C of EN-GINE CONDITION lever air start switch (1)

and specified terminal?

TestNO

Prop Sw TB-Term Points

1 S23S TB146A (3) -19337 38

2 S23T TB146A (3) -19437 38

3 S23U TB146A (3) -19537 38

4 S23V TB146A (3) -19637 38


177/693

TO 1C-130H-2-61FI-00-1

FROM SHT 13

464

Check NTS linkage (1) for correctgap of 0 011 to 0 020 inch in ac NO


178/693

gap of 0.011 to 0.020 inch in ac- NOcordance with TO 1C-130H-2-61JG-20-1, 61-20-22.

Is adjustment correct?

YES

465

Inspect NTS linkage through valveYES

housing assembly cover (2) forevidence of binding.Is any binding observed?

NO


179/693

TO 1C-130H-2-61FI-00-1

FROM SHT 13

469YES

Did propeller feather override but- TO SHT 153ton (3) pull in?


180/693

ton (3) pull in?

NO

470

Temporarily remove power fromairplane and gain access to termi-nals of propeller feather override

YESbutton.Is 28 VDC present on button ter-minal 1?

26


181/693

TO 1C-130H-2-61FI-00-1

477FROM SHT 149

Rep474

nal HTemporarily remove power from airplane boarand gain access to terminals of fire emer- 12 )


182/693

and gain access to terminals of fire emer 12.)YES

gency handle switch (3).Is 28 VDC present on switch terminal H1? Prop

143 234NO

475

478Is 28 VDC present on switch terminal G1? YES

Rep42

NO


183/693

TO 1C-130H-2-61FI-00-1

FROM SHT 149

481


184/693

Gain access to and disconnectplug P391 (3) at feather solenoid YES

valve.Is 28 VDC present between plugpins A and B?

19 18

NO

484

a. Open EMER FEATHER circuit


185/693

TO 1C-130H-2-61FI-00-1

FROM SHT 153

489NO

Is airplane being troubleshot a C-130B model through AF59-5957?


186/693

g

YES

490

Gain access to terminal boardTB115L (2).Is 28 VDC present on specified ter-minal?

Test

YESProp TB-Term Point


187/693

TO 1C-130H-2-61FI-00-1


188/693


189/693

TO 1C-130H-2-61FI-00-1


190/693


191/693

TO 1C-130H-2-61FI-00-1

FROM SHT 19

511 6110006

a. Shut down engines (1) in ac-cordance with TO 1C-130H-2-71JG 00 1 71 00 10 or TO 1C


192/693

71JG-00-1, 71-00-10; or TO 1C-NO

130(A)H-2-71JG-00-1, 71-00-10.b. Check throttle control systemrigging in accordance with TO 1C-130H-2-76JG-00-1, 76-10-01.Is rigging correct?

YES

512

Check engine coordinator-to-pro-

peller control assembly rigging in NO


193/693

TO 1C-130H-2-61FI-00-1

FROM SHT 19

520

Did RPM increase to 103.5 per- YEScent or above and hold when fuel TO SHT 165governing switch (1) was held in


194/693

governing switch (1) was held inCHECK during pitchlock check?

NO

523

521 Perform propeller synchrophasercheck in accordance with TO 1C-NO NDid RPM increase at all when fuel130H-2-61JG-10-1, 61-10-02governing switch was held in(subtask 1-2-9).CHECK during pitchlock check?Is synchrophaser check satisfac-

tory?YES


195/693

TO 1C-130H-2-61FI-00-1

FROM SHT 163

529

Remove dome assembly in accor-dance with TO 1C-130H-2-61JG-

NO10-1 61-10-11


196/693

10 1, 61 10 11.Is pin on ratchet ring (1) alignedwith etch mark on lip of No. 2

blade barrel bore (2)?

YES


197/693

TO 1C-130H-2-61FI-00-1

FROM SHT 21

532 6110003

a. Shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-


198/693

00 1, 71 00 10; TO 1C 130(A)H2-71JG-00-1, 71-00-10; or TO 1C-130(M)H-2-71JG-00-1, 71-00-10.

b. Move engine condition lever (2)to FEATHER/FTR.

NOc. After propeller blades (1) havereached feather position, checkfor internal leakage by holdingpropeller feather override button(3) in while listening for a loudsqueal from respective propellerassembly.Is a loud squeal heard from pro-peller?


199/693

TO 1C-130H-2-61FI-00-1

FROM SHT 21

537 6110001

Perform inspection for loose propellerYES

blades in accordance with TO 1C-130H-2-61JG-10-1, 61-10-22.


200/693

,Are any loose blades found?

NO

538

Perform inspection of propeller bladeNO

tracking in accordance with TO 1C-130H-2-61JG-10-1, 61-10-23.Is tracking satisfactory?

YES


201/693

TO 1C-130H-2-61FI-00-1

FROM SHT 169

549

Inspect engine condition controlsystem for loose, worn, or brokencomponents in accordance with YES


202/693

TO 1C-130H-2-76JG-00-1, 76-10-03, 76-10-11, and 76-10-12; or

TO 2J-T56-56, as required.Are any discrepancies found?

NO

550

Inspect throttle control system forloose, worn, or broken compo-

nents in accordance with TO 1C YES


203/693

TO 1C-130H-2-61FI-00-1


204/693


205/693

TO 1C-130H-2-61FI-00-1

FROM SHT 1

10


206/693

Check affected propeller assem-blies for correct fluid level in ac-

NOcordance with TO 1C-130H-2-12JG-10-2, 12-16-03.Is fluid level in one propeller as-sembly low?

YES


207/693

TO 1C-130H-2-61FI-00-1


208/693


209/693

TO 1C-130H-2-61FI-00-1

FROM SHT 1

22 6110032

Momentarily hold the MACAWSLAMP TEST switch (4) in the test NOposition.Does the applicable PROP light


210/693

Does the applicable PROP light(1) come on?

YES

23

Gain access to related diode CR3(2).Is voltage present on terminal ( )of diode CR3?


211/693

TO 1C-130H-2-61FI-00-1

FROM SHT 7

27

Is voltage present on cathode of diode CR3 (2)?

Test


212/693

TestProp Diode Point

29YES

1 CR3GB74

Replace

2 CR3GC75

3 CR3GD76

4 CR3GE77

NO


213/693

TO 1C-130H-2-61FI-00-1


214/693


215/693

TO 1C-130H-2-61FI-00-1

FROM SHT 11

40

Inspect wiring to propeller controlYES

receptacle (2) (for plug P392) forloose and broken connections.Is any damage found?


216/693

NO

41

Gain access to oil level indicatorswitch (1) and disconnect wiresfrom switch.Is a ground present on discon- YESnected wires?


217/693

TO 1C-130H-2-61FI-00-1

FROM SHT 11

45

Gain access to and disconnect applicable wirefrom diode CR3 (2).Is a ground present on disconnected wire?


218/693

Wire Test 47YESProp Diode 1 Diode 2 No. PointIs an outboard propellerbeing troubleshot?

1 CR3AX CR3FX 1E600D14

2 CR3AY CR3FY 2E600C16

3 CR3AZ CR3FZ 3E600C18

4 CR3BA CR3GA 4E600D20

YES


219/693

TO 1C-130H-2-61FI-00-1

FROM SHT 15

52 YESTO SHT 21

Is airplane an MC-130H?

NO


220/693

53

Remove diode CR3 (2) associat-ed with propeller position.Is a ground present on diode bus 54bar?

Gain access to terminals of in-dicator lights dimmer No. 7 (3)

Testand disconnect wire from dim-YES YESProp Diode Pointmer terminal e.Is a ground present on discon-

1 CR3AX13


221/693

TO 1C-130H-2-61FI-00-1

FROM SHT 15

58

Remove diode CR3 (3) associat-ed with propeller position.Is a ground present on diode busbar?


222/693

TestProp Diode Point YES

1 CR3FX13

2 CR3FY15

3 CR3FZ17

4 CR3GA19


223/693

TO 1C-130H-2-61FI-00-1

FROM SHT 17

63

Remove diode CR3 (1) associated with propel-ler position.Is a ground present on diode bus bar?

Prop Diode Test Point


224/693

Prop Diode Test PointNO

TO SHT 231 CR3AX 13

2 CR3AY15

3 CR3AZ17

4 CR3BA19

YES


225/693

TO 1C-130H-2-61FI-00-1

FROM SHT 21

6870Is ground present on specified pin of plug

47407A1P1 and 40407A2P1 of indicator Replight dimmer No. 7 (2)? of P

lightProp Pin Test Point 4740


226/693

Prop Pin Test Point 4740lightYES

1 47407A1P1-10 102

Prop2 47407A1P1-24

10112

3 47407A1P1-2399

34

4 47407A2P1-1083

NO


227/693

TO 1C-130H-2-61FI-00-1

FROM SHT 21

7573

RepGain access to terminals of PROP

masLOW OIL QUANTITY master warning

fied light (3) and disconnect wire from

PELNOlight terminal 2.

that Is a ground present on disconnected


228/693

s a g ou d p ese t o d sco ectedwire?

Prop1492

YES

76

Rep74

pin CGain access to and disconnect plugs mas


229/693

TO 1C-130H-2-61FI-00-1

FROM SHT 17

78

Gain access to terminals of indi-cator lights dimmer No. 7 (3) anddisconnect wire from specifieddimmer terminal.Is a ground present on discon-


230/693

g pnected wire?

Dim TestYES

Prop Term Point

1 A7

2 B5

3 C3

1


231/693

TO 1C-130H-2-61FI-00-1

FROM SHT 17

83

Gain access to terminals of PROPLOW OIL QUANTITY masterwarning light (2) and disconnect

NOwire from light terminal 2.Is a ground present on discon-


232/693

nected wire?

49

YES

84

Gain access to and disconnect


233/693

TO 1C-130H-2-61FI-00-1

FROM SHT 5

88

With engine(s) running, hold en-gine condition lever (2) to AIR YESSTART for 15 seconds.Does PROPELLER LOW OILWARNING/PROP light (1) go off?


234/693

WARNING/PROP light (1) go off?

NO

89

a. Shut down engine(s) in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-2-71JG-00-1, 71-00-10; or TO 1C-

NO


235/693

TO 1C-130H-2-61FI-00-1


236/693


237/693

TO 1C-130H-2-61FI-00-1

FROM SHT 33

102

Gain access to and disconnect plug47407A2P1 from indicator light dimmer No.7 (2). NOIs a ground present on pin 16 of plug TO SHT 3747407A2P1?


238/693

86

YES

103 105

Is airplane equipped with a flight data re- RepNO

corder system? (Check for presence of plug


239/693

TO 1C-130H-2-61FI-00-1

FROM SHT 35

108

Is a ground present on pin 24 of plug47404A2P1 of indicator light dimmer No. 7 110NO(4)?

Rep

82


240/693

YES

109

Gain access to and disconnect plug P251 111(2) at main instrument panel disconnect.

RepIs a ground present on pin C of receptacle NO

plugJ129 (1)?

No


241/693

TO 1C-130H-2-61FI-00-1

FROM SHT 33

113

Disconnect wire from terminal Eof indicator lights dimmer No. 7(3). NOIs a ground present on discon-nected wire?


242/693

9

YES

114

Gain access to and disconnectplug P251 (1) at main instrumentpanel disconnect. NO


243/693

TO 1C-130H-2-61FI-00-1


244/693


245/693

TO 1C-130H-2-61FI-00-1

FROM SHT 41

128NO

Is an outboard propeller beingtroubleshot?

YES


246/693

129

Gain access to and disconnectNO

plug P130/P1139 (4) at outer


247/693

TO 1C-130H-2-61FI-00-1

FROM SHT 1

133

Press to test affected PROPEL- 137YES NLER LOW OIL WARNING light (1

Is airplane an MC-130H?or 2).Does light press to test?

NO

YES


248/693

TO SHT 47

134

Temporarily remove power andgain access to terminals of affect-ed PROPELLER LOW OIL

YESWARNING light.


249/693

TO 1C-130H-2-61FI-00-1

FROM SHT 45

141

a. Open PROP LOW OIL LEVEL circuitbreaker (2).b. Gain access to and disconnect plugs

14347407A1P1 and 47407A2P1 from indicatorlight dimmer No. 7 (4). RepIs ground present on specified pin of plug pin o


250/693

47407A1P1 and 40407A2P1 of indicator of inlight dimmer No. 7? ed d

NO

Prop Pin Test Point Prop1

1 47407A1P1-491

23

2 47407A1P1-1693

4

3 47407A1P1-1595


251/693

TO 1C-130H-2-61FI-00-1

FROM SHT 45

146

a. Open PROP LOW OIL LEVELcircuit breaker (2).b. Gain access to terminals of in-dicator lights dimmer No. 7 (4).Is a ground present on specifieddimmer terminal?


252/693

Dim TestNO

Prop Term Point

1 a8

2 b6

3 c4

4 d2


253/693

TO 1C-130H-2-61FI-00-1

FROM SHT 451

151R

Is No. 2 PROPELLER LOW OIL 1YESWARNING light (2) being Wtroubleshot? N

INNO


254/693

1152

RPress to test No. 2 PROPELLER 1NOLOW OIL WARNING light. WDoes light press to test? N

INYES

1


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TO 1C-130H-2-61FI-00-1

FROM SHT 1163

Temporarily remove power and ga160 6110031cess to terminals of PROP LOW ONOPress to test PROP LOW OIL QUANTI-QUANTITY master warning light.

TY master warning light (2).Is 28 VDC present on light termin

Does light press to test?

48YES

NO

7/28/2019 134466125 to 1C 130H 2 61FI 00

134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130...

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Transcript of 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130...